燃气涡轮试验与研究
燃氣渦輪試驗與研究
연기와륜시험여연구
GAS TURBINE EXPERIMENT AND RESEARCH
2014年
5期
43-48
,共6页
赵秋月%娄德仓%郭文%王代军
趙鞦月%婁德倉%郭文%王代軍
조추월%루덕창%곽문%왕대군
航空发动机%管式减涡器%旋转盘腔%鼓筒孔%压力损失%流动特性%数值模拟
航空髮動機%管式減渦器%鏇轉盤腔%鼓筒孔%壓力損失%流動特性%數值模擬
항공발동궤%관식감와기%선전반강%고통공%압력손실%류동특성%수치모의
aero-engine%tubed vortex reducer%rotating cavity%offtake passage%pressure losses%flow characteristic%numerical simulation
对带有管式减涡器的盘腔内流动特性进行数值模拟,研究了减涡管的长度、管径和引气鼓筒孔的外形及尺寸,对盘腔内压力损失、流动结构的影响。计算结果表明:管式减涡器对于降低引气气流的压力损失有显著作用,存在最佳的减涡管长度使得引气的压力损失最小;减涡管管径、鼓筒孔面积增大都会减少流动损失;在鼓筒孔面积一定的情况下,长圆形鼓筒孔的性能比圆形鼓筒孔的更优。
對帶有管式減渦器的盤腔內流動特性進行數值模擬,研究瞭減渦管的長度、管徑和引氣鼓筒孔的外形及呎吋,對盤腔內壓力損失、流動結構的影響。計算結果錶明:管式減渦器對于降低引氣氣流的壓力損失有顯著作用,存在最佳的減渦管長度使得引氣的壓力損失最小;減渦管管徑、鼓筒孔麵積增大都會減少流動損失;在鼓筒孔麵積一定的情況下,長圓形鼓筒孔的性能比圓形鼓筒孔的更優。
대대유관식감와기적반강내류동특성진행수치모의,연구료감와관적장도、관경화인기고통공적외형급척촌,대반강내압력손실、류동결구적영향。계산결과표명:관식감와기대우강저인기기류적압력손실유현저작용,존재최가적감와관장도사득인기적압력손실최소;감와관관경、고통공면적증대도회감소류동손실;재고통공면적일정적정황하,장원형고통공적성능비원형고통공적경우。
CFD studies have been performed on the flow characteristics in rotating cavity with tubed vortex reducer. Particular attention was paid to the influence of length and diameter of the tubes along with configu-ration and size of the offtake passage cross sections on the pressure losses and the flow field. The results show that tubed vortex reducers perform well with respect to reducing pressure losses and there exists an op-timum length of the tube. As a rule, the pressure loss decreases with bigger diameter of the tubes and area of the offtake sections, tubed vortex reducers with slotted offtake cross sections perform better than those with circular sections with the same area.